@article{MAKHILLJEAS201813215446,
    title = {Integral Modified Linear Quadratic Regulator Method for Controlling
Lateral Movement of Flying Wing in Rotational Roll Mode},
    journal = {Journal of Engineering and Applied Sciences},
    volume = {13},
    number = {2},
    pages = {463-471},
    year = {2018},
    issn = {1816-949x},
    doi = {jeasci.2018.463.471},
    url = {https://makhillpublications.co/view-article.php?issn=1816-949x&doi=jeasci.2018.463.471},
    author = {Tri Kuntoro},
    keywords = {Autonomous flight control,integral modified LQR,stability,steady state error,experiments,UAV},
    abstract = {The studies on fix wing Unmanned Aerial Vehicle (UAV), especially, flying wing type has progressed
very rapidly. Therefore, fix-wing UAV can be used to support disaster mitigation and monitoring. But in order
to make UAV completes the mission, it needs an autonomus flight control system. There were two types of
control method in order to control the movement of flying wing, i.e., longitudinal and lateral. Control of lateral
motion is considered more important because it serves to prevent air turbulence that can cause the air to move
is not in accordance with the mission that has been set. This research aims to design control lateral movement
that is focused on using the roll rotational motion mode control method Linear Quadratic Regulator (LQR) with
the addition of integral in dealing with steady state error that occurred. Experiments conducted by simulating
the model airframe using DATCOM and control simulation using MATLAB. The results showed that by using
modifeied LQR control with integral components added, the system is able to stabilize the rotational motion roll
in a short time and minimal overshoot. In addition, the experiment also showed that steady-state error in the
system can be eliminated with a rise time = 0.189 sec, overshoot = 0.688%, settling time = 0.301 sec and steady
state error = 0%.}
    }